Cabin air compressor support bracket

ABSTRACT

A support bracket for a cabin air compressor (CAC) assembly includes a CAC mounting portion with a plurality of CAC mounting holes distributed in an arc configuration along a CAC mounting hole circle radius. A support portion includes a ramped face that transitions to an upper lug portion and a substantially perpendicular face relative to the CAC mounting portion. An upper lug extends from the upper lug portion. The upper lug includes a coupling hole that is offset from a first CAC mounting hole of the CAC mounting holes at a length in a first direction and a length in a second direction. A ratio of the CAC mounting hole circle radius to the length in the first direction is between 2.14 and 2.20, and a ratio of the CAC mounting hole circle radius to the length in the second direction is between 1.16 and 1.19.

BACKGROUND OF THE INVENTION

The subject matter disclosed herein relates to aircraft environmentalcontrol. More specifically, the subject disclosure relates to a supportbracket of a cabin air compressor for an aircraft environmental controlsystem.

Environmental control systems (ECSs) are utilized on various types ofaircraft for several purposes, such as in cooling systems for theaircraft. For example, components of an ECS may be utilized to removeheat from various aircraft lubrication and electrical systems and/orused to condition aircraft cabin air. A cabin air conditioning andtemperature control system (CACTCS) is an example of an aircraft ECSthat includes air cycle packs supplied with pressurized outside (fresh)air from electric motor-driven cabin air compressors (CACs) whichcondition fresh air for cabin heating and cooling. The CACTCS providesflow control for modulation of cooling pack air flow, recirculation fansto circulate cabin air, and associated valves and sensors used forsystem control.

The CACTCS may also include a trim air system to provide individualcabin zone temperature control. This includes trim temperature controlvalves, trim duct heaters and associated sensors. As one example, aCACTCS may provide control of six baseline passenger zones and a flightdeck zone. Additional zones, such as a forward cargo zone, a crew zoneand/or an attendant zone may be controlled by other ECSs. Recirculationfans may also be provided for additional air flow to the passenger cabinand to ensure that flow at an air distribution nozzle remains constant.

Various elements of aircraft ECSs can experience harsh environmentsincluding a wide range of temperatures, pressures, and vibrations.Elements of aircraft ECSs must also fit within a compact space andminimize weight while providing adequate strength to handle typical andpeak stresses over the anticipated life of the elements.

BRIEF DESCRIPTION OF THE INVENTION

According to one aspect, a support bracket for a cabin air compressorassembly is provided. The support bracket includes a cabin aircompressor mounting portion with a plurality of cabin air compressormounting holes distributed in an arc configuration along a cabin aircompressor mounting hole circle radius. A support portion includes aramped face that transitions to an upper lug portion and a substantiallyperpendicular face relative to the cabin air compressor mountingportion. An upper lug extends from the upper lug portion. The upper lugincludes a coupling hole that is offset from a first cabin aircompressor mounting hole of the cabin air compressor mounting holes at alength in a first direction and a length in a second direction. A ratioof the cabin air compressor mounting hole circle radius to the length inthe first direction is between 2.14 and 2.20, and a ratio of the cabinair compressor mounting hole circle radius to the length in the seconddirection is between 1.16 and 1.19.

According to another aspect, a cabin air compressor support assemblyincludes a left-hand cabin air compressor support bracket coupled to acabin air compressor assembly and an upper three-way mount. The cabinair compressor support assembly also includes a right-hand cabin aircompressor support bracket coupled to the cabin air compressor assemblyand a lower three-way mount. The right-hand cabin air compressor supportbracket includes a cabin air compressor mounting portion with aplurality of cabin air compressor mounting holes distributed in an arcconfiguration along a cabin air compressor mounting hole circle radius.A support portion includes a ramped face that transitions to an upperlug portion and a substantially perpendicular face relative to the cabinair compressor mounting portion. An upper lug extends from the upper lugportion. The upper lug includes a coupling hole that is offset from afirst cabin air compressor mounting hole of the cabin air compressormounting holes at a length in a first direction and a length in a seconddirection. A ratio of the cabin air compressor mounting hole circleradius to the length in the first direction is between 2.14 and 2.20,and a ratio of the cabin air compressor mounting hole circle radius tothe length in the second direction is between 1.16 and 1.19.

According to a further aspect, a method of installing a support bracketin a cabin air conditioning and temperature control system includescoupling an upper lug of the support bracket to a mount of the cabin airconditioning and temperature control system. A cabin air compressormounting portion of the support bracket is coupled to a cabin aircompressor assembly of the cabin air conditioning and temperaturecontrol system. The support bracket includes the cabin air compressormounting portion with a plurality of cabin air compressor mounting holesdistributed in an arc configuration along a cabin air compressormounting hole circle radius. A support portion includes a ramped facethat transitions to an upper lug portion and a substantiallyperpendicular face relative to the cabin air compressor mountingportion. The upper lug extends from the upper lug portion. The upper lugincludes a coupling hole that is offset from a first cabin aircompressor mounting hole of the cabin air compressor mounting holes at alength in a first direction and a length in a second direction. A ratioof the cabin air compressor mounting hole circle radius to the length inthe first direction is between 2.14 and 2.20, and a ratio of the cabinair compressor mounting hole circle radius to the length in the seconddirection is between 1.16 and 1.19.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a partial perspective view of a cabin air conditioning andtemperature control system;

FIG. 2 is another partial perspective view of the cabin air conditioningand temperature control system of FIG. 1;

FIG. 3 is a perspective view of a cabin air compressor support bracket;

FIG. 4 is another view of the cabin air compressor support bracket ofFIG. 3;

FIG. 5 is another view of the cabin air compressor support bracket ofFIG. 3; and

FIG. 6 is a side view of the cabin air compressor support bracket ofFIG. 3.

DETAILED DESCRIPTION OF THE INVENTION

Shown in FIGS. 1 and 2 are partial perspective views of a cabin airconditioning and temperature control system (CACTCS) 100. The CACTCS 100includes an upper three-way mount 102 with coupling points 104 a and 104b. The upper three-way mount 102 may also be coupled to one or morevibration isolators 106. The coupling point 104 b is coupled to a firstcabin air compressor (CAC) support bracket 108 which is also coupled toa CAC 110. A second CAC support bracket 114 is coupled to the CAC 110and a coupling point 116 b of a lower three-way mount 118 as best viewedin FIG. 2. Similar to the upper three-way mount 102, the lower three-waymount 118 includes a pair of coupling points 116 a and 116 b. The firstCAC support bracket 108 and the second CAC support bracket 114collectively form a CAC support assembly 120. The first CAC supportbracket 108 may also be referred to as a left-hand CAC support bracket,and the second CAC support bracket 114 may be referred to as aright-hand CAC support bracket. The coupling points 104 a and 116 a maybe used to support a second CAC (not depicted), where the CAC 110 may bereferred to as an inner CAC and the second CAC (not depicted) may bereferred to as an outer CAC. The three-way mounts 102 and 118 limit CACmovement in three directions (X-Y-Z).

FIG. 3 is a perspective view of the second CAC support bracket 114 ofFIGS. 1 and 2. The second CAC support bracket 114 includes a CACmounting portion 350, a support portion 352, an upper lug portion 356,and an upper lug 358. The support portion 352 includes a ramped face 354that transitions to the upper lug portion 356. The support portion 352also includes a substantially perpendicular face 360 relative to the CACmounting portion 350. The CAC mounting portion 350 includes a first CACmounting hole 362, a second CAC mounting hole 364, and a third CACmounting hole 366 distributed in an arc configuration. The CAC mountingholes 362 and 366 are also referred to as the outermost CAC mountingholes 362 and 366 relative to the CAC mounting hole 364. A curvedtransition region 368 is formed between the substantially perpendicularface 360 and the CAC mounting portion 350. An inner angled edge 370 andan outer angled edge 372 are defined along the substantiallyperpendicular face 360 between the CAC mounting portion 350 and theupper lug portion 356, where the outer angled edge 372 is an edge of theramped face 354. A curved transition region 374 is formed between theupper lug portion 356 and the upper lug 358. The upper lug 358 extendsfrom the upper lug portion 356 and includes a coupling hole 378.

The CAC mounting holes 362-366 are configured to mate the second CACsupport bracket 114 to the CAC 110 of FIG. 1. The coupling hole 378 isconfigured to mate the second CAC support bracket 114 with the couplingpoint 116 b of FIG. 1.

FIG. 4 is another view of the CAC support bracket 114 depicting thesubstantially perpendicular face 360 of the support portion 352 and sideviews of the CAC mounting portion 350, the upper lug 358, and the curvedtransition region 374. A datum A defines a reference on the CAC mountingportion 350, and centerline B (CLB) defines a centerline through CACmounting hole 362. Datum A is defined on a non-CAC side 375 of the CACmounting portion 350 that is opposite a CAC side 373 that is in closerproximity to the CAC 110 of FIG. 1 upon coupling the CAC support bracket114 to the CAC 110 of FIG. 1.

An angle θ1 of about 21.5 degrees is defined between datum A at CLB anda reference line 376 formed parallel to the outer angled edge 372. Theouter angled edge 372 and the reference line 376 are separated by alength L1 of about 0.81 inches (2.057 cm). A reference line 377 isdefined as an extension of the inner angled edge 370, and anotherreference line 379 is defined parallel to the reference line 377. Anangle θ2 of about 51.5 degrees is defined between datum A at CLB and thereference line 379. The reference lines 377 and 379 are separated by alength L2 of about 3.33 inches (8.458 cm). A length L3 of about 3.07inches (7.798 cm) is defined between datum A and an outer face 380 ofthe upper lug portion 356. A length L4 of about 3.351 inches (8.5115 cm)is defined between datum A and an outer face 381 of the upper lug 358.In an embodiment, the CAC mounting portion 350 has a thickness T1 ofabout 0.355 inches (0.9017 cm), and the upper lug 358 has a thickness T2of about 0.815 inches (2.0701 cm).

FIG. 5 is a detailed view of the CAC mounting portion 350 of the CACsupport bracket 114. The CAC mounting holes 362, 364, and 366, eachhaving a diameter D1 of about 0.406 inches (1.0312 cm), are distributedin an arc configuration along a CAC mounting hole circle radius R1 ofabout 8.375 inches (21.2725 cm) proximate a curved edge 382. The CACmounting hole circle radius R1 is defined from an origin O. Relative toCLB, CAC mounting hole 364 is offset by an angle θ3 of about 15 degrees,and CAC mounting hole 366 is offset by an angle θ4 of about 30 degreesat the CAC mounting hole circle radius R1. A pair of orthogonalreference lines 384 and 386 intersects at CLB. Another pair oforthogonal lines 388 and 390 intersects at the coupling hole 378. Alength L5 of about 1.76 inches (4.470 cm) is defined between thereference line 384 and the substantially perpendicular face 360.

A length L6 of about 3.863 inches (9.812 cm) is defined in a firstdirection between reference lines 384 and 388. A length L7 of about7.112 inches (18.0645 cm) is defined in a second direction between thereference lines 386 and 390. Reference line 384 is offset by a length L8of about 7.88 inches (20.015 cm) from the origin O, and reference line386 is offset by a length L9 of about 2.837 inches (7.206 cm) from theorigin O. An outer edge 392 of the CAC mounting portion 350 that isproximate to the CAC mounting hole 362 is offset at an angle θ5 of about56.67 degrees relative to the substantially perpendicular face 360.

The ramped face 354 has an angled edge 394 defined at an angle θ6 ofabout 25.15 degrees relative to the reference line 384 and offset by alength L10 of about 1.645 inches (4.178 cm). A corner 396 is defined atan outer edge of the substantially perpendicular face 360 and the upperlug portion 356 proximate an angled edge 398 of the upper lug portion356. A length L11 of about 6.5 inches (16.51 cm) is defined between thecorner 396 and the reference line 386. The angled edge 398 is offset atan angle θ7 of about 49.1 degrees relative to the reference line 388.

The coupling hole 378 has a diameter D2 of about 0.6375 inches (1.6193cm) and is configured to receive a bushing 400. The bushing 400 providesa bearing portion for a fastener (not depicted) to engage with thecoupling point 116 b of FIG. 1. The upper lug 358 has a diameter D3 ofabout 1.50 inches (3.81 cm).

FIG. 6 is a side view of the CAC support bracket 114. The angled edge394 extends along the support portion 352 to an end 402 proximate CLB.The end 402 is offset by a length L12 of about 1.385 inches (3.518 cm)from CLB at datum A.

A number of ratios are defined between elements of the support bracket114 as depicted in FIGS. 1-6. In an embodiment, a ratio of the CACmounting hole circle radius R1 to the length L6 in the first directionis between 2.14 and 2.20, and a ratio of the CAC mounting hole circleradius R1 to the length L7 in the second direction is between 1.16 and1.19. A ratio of the angle θ4 defined between the first and third CACmounting holes 362 and 366 at the CAC mounting hole circle radius R1relative to the angle θ3 defined between the first and second CACmounting holes 362 and 364 at the CAC mounting hole circle radius R1 isbetween 1.90 and 2.11. A ratio of the CAC mounting hole circle radius R1to the thickness T1 of the CAC mounting portion 350 is between 22.17 and25.18. A ratio of the diameter D2 of the coupling hole 378 to thediameter D1 of the first CAC mounting hole 362 is between 1.53 and 1.62.A ratio of the diameter D3 of the upper lug 358 to the diameter D1 ofthe first CAC mounting hole 362 is between 3.58 and 3.82. A ratio of theCAC mounting hole circle radius R1 to the length L5 between the firstCAC mounting hole 362 and the substantially perpendicular face 360 isbetween 4.67 and 4.85. A ratio of the length L4 between datum A and theouter face 381 of the upper lug 358 relative to the length L3 betweendatum A and the outer face 380 of the upper lug portion 356 is between1.07 and 1.11.

A process of installing the CAC support bracket 114 in the cabin airconditioning and temperature control system 100 is described inreference to FIGS. 1-6. The upper lug 358 of the CAC support bracket 114is coupled to the coupling point 116 b of the lower three-way mount 118.The CAC mounting portion 350 of the CAC support bracket 114 is coupledto the CAC 110. The CAC support bracket 108 is also coupled to the CAC110 and to the coupling point 104 b of the upper three-way mount 102. Aspreviously described, the CAC support bracket 114 includes the CACmounting portion 350 with a plurality of CAC mounting holes 362-366distributed in an arc configuration along the CAC mounting hole circleradius R1. The support portion 352 includes the ramped face 354 thattransitions to the upper lug portion 356 and the substantiallyperpendicular face 360 relative to the CAC mounting portion 350. Theupper lug 358 extends from the upper lug portion 356. The upper lug 358includes the coupling hole 378 that is offset from a first CAC mountinghole 362 at the length L6 in a first direction and the length L7 in asecond direction. A ratio of the CAC mounting hole circle radius R1 tothe length L6 in the first direction is between 2.14 and 2.20, and aratio of the CAC mounting hole circle radius R1 to the length L7 in thesecond direction is between 1.16 and 1.19.

While the invention has been described in detail in connection with onlya limited number of embodiments, it should be readily understood thatthe invention is not limited to such disclosed embodiments. Rather, theinvention can be modified to incorporate any number of variations,alterations, substitutions or equivalent arrangements not heretoforedescribed, but which are commensurate with the spirit and scope of theinvention. Additionally, while various embodiments of the invention havebeen described, it is to be understood that aspects of the invention mayinclude only some of the described embodiments. Accordingly, theinvention is not to be seen as limited by the foregoing description, butis only limited by the scope of the appended claims.

The invention claimed is:
 1. A support bracket for a cabin aircompressor assembly, the support bracket comprising: a cabin aircompressor mounting portion comprising a plurality of cabin aircompressor mounting holes distributed in an arc configuration along acabin air compressor mounting hole circle radius; a support portioncomprising a ramped face that transitions to an upper lug portion and asubstantially perpendicular face relative to the cabin air compressormounting portion; and an upper lug extending from the upper lug portion,the upper lug comprising a coupling hole, wherein the coupling hole isoffset from a first cabin air compressor mounting hole of the cabin aircompressor mounting holes at a length in a first direction and a lengthin a second direction, a ratio of the cabin air compressor mounting holecircle radius to the length in the first direction is between 2.14 and2.20, and a ratio of the cabin air compressor mounting hole circleradius to the length in the second direction is between 1.16 and 1.19.2. The support bracket of claim 1, wherein the cabin air compressormounting holes further comprise a second cabin air compressor mountinghole and a third cabin air compressor mounting hole, and a ratio of anangle defined between the first and third cabin air compressor mountingholes at the cabin air compressor mounting hole circle radius relativeto an angle defined between the first and second cabin air compressormounting holes at the cabin air compressor mounting hole circle radiusis between 1.90 and 2.11.
 3. The support bracket of claim 1, wherein aratio of the cabin air compressor mounting hole circle radius to athickness of the cabin air compressor mounting portion is between 22.17and 25.18.
 4. The support bracket of claim 1, wherein a ratio of adiameter of the coupling hole to a diameter of the first cabin aircompressor mounting hole is between 1.53 and 1.62.
 5. The supportbracket of claim 1, wherein a ratio of a diameter of the upper lug to adiameter of the first cabin air compressor mounting hole is between 3.58and 3.82.
 6. The support bracket of claim 1, wherein a ratio of thecabin air compressor mounting hole circle radius to a length between thefirst cabin air compressor mounting hole and the substantiallyperpendicular face is between 4.67 and 4.85.
 7. The support bracket ofclaim 1, wherein a datum is defined on a non-cabin air compressor sideof the cabin air compressor mounting portion, and a ratio of a lengthbetween the datum and an outer face of the upper lug relative to alength between the datum and an outer face of the upper lug portion isbetween 1.07 and 1.11.
 8. A cabin air compressor support assemblycomprising: a left-hand cabin air compressor support bracket coupled toa cabin air compressor assembly and an upper three-way mount; and aright-hand cabin air compressor support bracket coupled to the cabin aircompressor assembly and a lower three-way mount, the right-hand cabinair compressor support bracket comprising: a cabin air compressormounting portion comprising a plurality of cabin air compressor mountingholes distributed in an arc configuration along a cabin air compressormounting hole circle radius; a support portion comprising a ramped facethat transitions to an upper lug portion and a substantiallyperpendicular face relative to the cabin air compressor mountingportion; and an upper lug extending from the upper lug portion, theupper lug comprising a coupling hole, wherein the coupling hole isoffset from a first cabin air compressor mounting hole of the cabin aircompressor mounting holes at a length in a first direction and a lengthin a second direction, a ratio of the cabin air compressor mounting holecircle radius to the length in the first direction is between 2.14 and2.20, and a ratio of the cabin air compressor mounting hole circleradius to the length in the second direction is between 1.16 and 1.19.9. The cabin air compressor support assembly of claim 8, wherein thecabin air compressor mounting holes further comprise a second cabin aircompressor mounting hole and a third cabin air compressor mounting hole,and a ratio of an angle defined between the first and third cabin aircompressor mounting holes at the cabin air compressor mounting holecircle radius relative to an angle defined between the first and secondcabin air compressor mounting holes at the cabin air compressor mountinghole circle radius is between 1.90 and 2.11.
 10. The cabin aircompressor support assembly of claim 8, wherein a ratio of the cabin aircompressor mounting hole circle radius to a thickness of the cabin aircompressor mounting portion is between 22.17 and 25.18.
 11. The cabinair compressor support assembly of claim 8, wherein a ratio of adiameter of the coupling hole to a diameter of the first cabin aircompressor mounting hole is between 1.53 and 1.62.
 12. The cabin aircompressor support assembly of claim 8, wherein a ratio of a diameter ofthe upper lug to a diameter of the first cabin air compressor mountinghole is between 3.58 and 3.82.
 13. The cabin air compressor supportassembly of claim 8, wherein a ratio of the cabin air compressormounting hole circle radius to a length between the first cabin aircompressor mounting hole and the substantially perpendicular face isbetween 4.67 and 4.85.
 14. The cabin air compressor support assembly ofclaim 8, wherein a datum is defined on a non-cabin air compressor sideof the cabin air compressor mounting portion, and a ratio of a lengthbetween the datum and an outer face of the upper lug relative to alength between the datum and an outer face of the upper lug portion isbetween 1.07 and 1.11.
 15. A method of installing a support bracket in acabin air conditioning and temperature control system comprising:coupling an upper lug of the support bracket to a mount of the cabin airconditioning and temperature control system; and coupling a cabin aircompressor mounting portion of the support bracket to a cabin aircompressor assembly of the cabin air conditioning and temperaturecontrol system, the support bracket comprising: the cabin air compressormounting portion comprising a plurality of cabin air compressor mountingholes distributed in an arc configuration along a cabin air compressormounting hole circle radius; a support portion comprising a ramped facethat transitions to an upper lug portion and a substantiallyperpendicular face relative to the cabin air compressor mountingportion; and the upper lug extending from the upper lug portion, theupper lug comprising a coupling hole, wherein the coupling hole isoffset from a first cabin air compressor mounting hole of the cabin aircompressor mounting holes at a length in a first direction and a lengthin a second direction, a ratio of the cabin air compressor mounting holecircle radius to the length in the first direction is between 2.14 and2.20, and a ratio of the cabin air compressor mounting hole circleradius to the length in the second direction is between 1.16 and 1.19.16. The method of claim 15, wherein the cabin air compressor mountingholes further comprise a second cabin air compressor mounting hole and athird cabin air compressor mounting hole, and a ratio of an angledefined between the first and third cabin air compressor mounting holesat the cabin air compressor mounting hole circle radius relative to anangle defined between the first and second cabin air compressor mountingholes at the cabin air compressor mounting hole circle radius is between1.90 and 2.11.
 17. The method of claim 15, wherein a ratio of the cabinair compressor mounting hole circle radius to a thickness of the cabinair compressor mounting portion is between 22.17 and 25.18.
 18. Themethod of claim 15, wherein a ratio of a diameter of the coupling holeto a diameter of the first cabin air compressor mounting hole is between1.53 and 1.62.
 19. The method of claim 15, wherein a ratio of the cabinair compressor mounting hole circle radius to a length between the firstcabin air compressor mounting hole and the substantially perpendicularface is between 4.67 and 4.85.
 20. The method of claim 15, wherein adatum is defined on a non-cabin air compressor side of the cabin aircompressor mounting portion, and a ratio of a length between the datumand an outer face of the upper lug relative to a length between thedatum and an outer face of the upper lug portion is between 1.07 and1.11.